Composite material wing integrated fuel tank structure

An integral fuel tank and composite material technology, applied in the directions of wings, aircraft parts, transportation and packaging, can solve the problems of inability to use large and medium-sized UAV structures, no lightning protection function, weak bearing capacity, etc., and achieve structural weight. Lightweight, easy to service and maintain, high load capacity

Active Publication Date: 2017-10-13
CAIHONG DRONE TECH CO LTD
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0002] In the existing large and medium-sized drones, there is no application of composite material integral fuel tanks. The composite material integral fuel tanks used in some small or micro-sized drones have small fuel capacity, weak carrying capacity, and no lightning protection function, so they cannot be used Large and medium UAV structure

Method used

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  • Composite material wing integrated fuel tank structure
  • Composite material wing integrated fuel tank structure
  • Composite material wing integrated fuel tank structure

Examples

Experimental program
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Embodiment

[0031] Preparation of composite material parts, including upper skin 2 and lower skin 4, and medium-temperature curing molding in an autoclave. When the upper skin 2 and the lower skin 4 are prepared, a metal mesh film is first pasted on the outer surface, and co-cured with the carbon fiber layup of the part to form, which greatly improves the conductivity of the composite skin and can have the function of lightning protection. The upper skin and the lower skin are made of carbon fiber composite material, as the main load-bearing structure, which can effectively reduce the structural weight.

[0032] After the parts are prepared, the surface treatment of the parts is carried out: the aluminum alloy parts are first anodized with chromic acid, and then coated with an anti-corrosion primer to improve the anti-corrosion ability of the aluminum alloy in the fuel medium; for the composite material parts, the inner surface is first sprayed with varnish, and then sprayed Antistatic co...

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Abstract

The invention discloses a composite material wing integrated fuel tank structure. The composite material wing integrated fuel tank structure comprises a front beam connector, upper skin, a front beam, lower skin, maintenance opening covers, a first wing rib, a rear beam connector, a second wing rib, a rear beam, a third wing rib and a fourth wing rib. Various components of an integrated fuel tank adopt mechanical connection; a bi-component polysulfide sealant is selected and used as a sealing agent. The wing integrated fuel tank structure is large in fuel capacity, light in structural weight, high in load capacity and convenient to maintain, and meanwhile, the composite material wing integrated fuel tank structure has good antistatic capacity and lightning protecting capacity.

Description

technical field [0001] The invention relates to an integral fuel tank structure of a composite material wing, which belongs to the technical field of unmanned aerial vehicle structures. Background technique [0002] In the existing large and medium-sized drones, there is no application of composite material integral fuel tanks. The composite material integral fuel tanks used in some small or micro-sized drones have small fuel capacity, weak carrying capacity, and no lightning protection function, so they cannot be used Large and medium drone structures. Contents of the invention [0003] The technical problem of the present invention is: to overcome the deficiencies of the prior art, to provide a composite wing integral fuel tank structure, which adopts a composite material skin and a metal frame, and forms a closed space through a sealed mechanical connection, which can maximize the utilization of the aircraft. The internal space of the wing is loaded with fuel, which ha...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/34
CPCB64C3/34
Inventor 李洪波燕德利王广博
Owner CAIHONG DRONE TECH CO LTD
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